function output = OT_LT(~,varargin)


%% Inputs
% Mass: Mass of spacecraft
% Thrust: Thrust level in N
% isp: Specific impulse
% tol_lat : Latitude tolerance
% tol_long : longitude tolerance
% target_long: Target longitude
% sim_day: Simulation Duration

numvarargs = length(varargin);
% Number of optional arguments

if mod(numvarargs, 2) == 1
    error('Error: Please check name-value pair arguments');
end
% Check for even number of name-value pair argments

% Defalut arguments

mass_sc = 50;
isp = 1500;
T = 0.039;
% COE_o = [25000,0.65,20,0,0,0];
COE_o = [24356,0.02,0.1,1,0,0];
COE_f = [7300,0.001,0.005,0,0,0];
eta = 0.9;
name_arguments = varargin(1:2:end);
value_arguments = varargin(2:2:end);
% Initialize name-value arguments

for ii = 1:length(name_arguments)
    switch lower(name_arguments{ii})
        case 'spacecraftmass'
            mass_sc = value_arguments{ii};
        case 'thrust'
            T = value_arguments{ii};
        case 'specificimpulse'
            isp = value_arguments{ii};
        case 'initialcoe'
            COE_o = value_arguments{ii};
        case 'finalcoe'
            COE_f = value_arguments{ii};
        case 'thrusteff'
            eta = value_arguments{ii};
    end
end

[massProp, flightTime, thrustTime, eclipseTime, coastTime,position] = Low_Thrust_main(mass_sc,T,isp,COE_f,COE_o,eta);

output.massProp = massProp;
output.flightTime = flightTime;
output.thrustTime = thrustTime;
output.eclipseTime = eclipseTime;
output.coastTime = coastTime;
output.position = position;

end
